An immersed boundary method [1]}, [2]} is used to resolve the flow past a 6:1 prolate spheroid at zero angle of attack. A numerical bump is introduced on the surface of the body to accelerate the transition of the boundary layer to turbulence. The annular bump is located where the surface favorable pressure gradient is nearly zero. This location is found at approximately \(0.5 D\)  from the nose. The radial extent of the bump is \(0.002 D\)  (\(\sim \)  15 wall units) and the streamwise extent is \(0.1 D\) .
